EP1496198B1 - Wellen- und Lageranordnung für eine dampfgekühlte Gasturbine - Google Patents

Wellen- und Lageranordnung für eine dampfgekühlte Gasturbine Download PDF

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Publication number
EP1496198B1
EP1496198B1 EP04023742A EP04023742A EP1496198B1 EP 1496198 B1 EP1496198 B1 EP 1496198B1 EP 04023742 A EP04023742 A EP 04023742A EP 04023742 A EP04023742 A EP 04023742A EP 1496198 B1 EP1496198 B1 EP 1496198B1
Authority
EP
European Patent Office
Prior art keywords
rotor
shaft portion
tail end
gas turbine
bearing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP04023742A
Other languages
English (en)
French (fr)
Other versions
EP1496198A2 (de
EP1496198A3 (de
Inventor
Takeaki c/o Takasago Mach. Works Oya
Kazuharu c/o Takasago Mach. Works Hirokawa
Tadateru c/o Takasago Mach. Works Tanioka
Katsunori c/o Takasago Mach. Works Tanaka
Kazuo c/o Takasago Mach. Works Uematsu
Tanehiro c/o Takasago R. & Dvpt. Cen. Shinohara
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from JP2000292763A external-priority patent/JP4690531B2/ja
Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Publication of EP1496198A2 publication Critical patent/EP1496198A2/de
Publication of EP1496198A3 publication Critical patent/EP1496198A3/de
Application granted granted Critical
Publication of EP1496198B1 publication Critical patent/EP1496198B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F01D25/125—Cooling of bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/60—Shafts
    • F05D2240/61—Hollow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam

Definitions

  • the invention relates to a bearing structure for bearing a shaft portion of a rotor tail end of a gas turbine, according to claim 1.
  • the present invention relates to prevention or restriction of thermal deformation of a rotor tail end of a steam-cooled gas turbine.
  • a so-called steam-cooled gas turbine in which the relatively low temperature of steam is used as a coolant, to protect stator blades and rotor blades of the gas turbine from the burnt gas of high temperature, in place of a conventional air cooling system, is being developed.
  • a rotor assembly of a gas turbine having a plurality of rotor disks which are fastened to each other by spindle bolts so as to rotate together is rotatably supported by a journal bearing. Since the rotor assembly of the gas turbine is very heavy, the gap between the shaft portion of the rotor assembly and the journal bearing is very precisely administrated. However, in the steam-cooled gas turbine, the steam passes through the center portion of the rotor assembly and, hence, the latter and in particularly its shaft portion is thermally deformed, so that the journal bearing can be damaged.
  • a bearing structure for bearing a shaft portion of a rotor tail end of a gas turbine having the features set out in claim 1, comprising: a rotor assembly of the gas turbine having a center axis; rotor blades of the gas turbine; a steam passage extending along the center axis for supplying and recovering a steam for cooling the rotor blades; a bearing pad which forms a journal bearing; and seal portions provided on opposite sides of the bearing pad in the axial direction to prevent leakage of a lubricant for lubricating a space between the bearing pad and the shaft portion, the width of said seal portion in the axial direction being such that the surface temperature of the shaft portion of the rotor tail end is maintained below a predetermined temperature by the lubricant, within the width of the bearing pad in the axial direction.
  • the seal portions provided on opposite sides of the bearing pad are made longer in the axial direction than that of the conventional seal portions, the lubricant supplied to a space between the shaft portion of the rotor tail end and the bearing pad can be spread over a broader surface area of the shaft portion in the axial direction. Consequently, a broader surface area of the shaft portion in the axial direction can be cooled by the lubricant, so that it is possible to maintain the surface temperature of the portion of the shaft portion that is opposed to the bearing pad, at a temperature below a predetermined value. Consequently, it is possible to restrict the thermal deformation, and particularly, the thermal expansion of the shaft portion in the radial direction, at the outer surface portion of the shaft portion that is opposed to the bearing pad, within an allowable limit.
  • Fig. 9 shows a known supply/recovery system of the cooling steam for rotor blades of a turbine.
  • the structure of the gas turbine rotor on the turbine side is completed by fastening a rotor tail end and a plurality of turbine disks.
  • the rotor tail end is provided with a center hole to define a coaxial steam pipe.
  • the rotor tail end 100 is provided with a substantially circular disk portion 120 which defines an end disk and a substantially cylindrical hollow shaft portion 140.
  • a disk center hole 130 and a rotor tail end center hole 150 extend along the central axis.
  • the disk portion 120 is provided with a plurality of through holes (not shown) which are spaced from one another in the circumferential direction at an equal distance.
  • a plurality of rotor blade disks (not shown) of the turbine are arranged in front of the disk portion 120 and, thereafter, turbine spindle bolts (not shown) are inserted in the through holes and fastened by nuts to form a rotor assembly in which the rotor blade disks (not shown) are supported and rotated together.
  • the disk center hole 130 of the rotor is provided with a steam passage member 200 welded thereto, through which the rotor blade cooling steam is supplied.
  • a passage to recover the steam for cooling the rotor blade is defined between the inner surface of the central hole 150 of the rotor tail end extending from the rear end of the end disk of the rotor into the shaft portion 140 of the rotor and the steam passage member, so that the steam used to cool the rotor blades by means of an appropriate cooling device (not shown) can be recovered.
  • the connection between the rotating rotor tail end 100 and the stationary part is established as follows.
  • the steam passage member 200 is connected to a stationary inner steam pipe 290 through a seal fin (labyrinth seal) 230.
  • a stationary short steam pipe 270 and an outer stationary steam pipe 280 are connected to the end of the rotor tail end 100 through a seal fin (labyrinth seal) 220.
  • the seal fins 220 and 230 are connected to a leakage steam recovery instrument (not shown).
  • the rotor assembly thus obtained is rotatably supported at the rotor tail end 100 thereof by a bearing 240.
  • the rotor blade cooling steam is produced by heating pressurized steam whose saturation temperature is approximately 140°C to 400°C or more, and is supplied through the passageway defined by the center hole of the rotor. Consequently, the rotor is heated to the saturation temperature of the cooling steam.
  • the tail end at which the bearing is provided is cooled by the lubricant to 100°C or less than 100°C, so that thermal deformation of the tail end occurs due to a temperature difference between the central hole and the tail end.
  • Fig. 1 shows a sectional view of a half of a tail end 10 of a rotor assembly of a gas turbine (which will be referred to merely as a rotator tail end), according to an embodiment not falling under the scope of the claims defining the invention.
  • the compressor side of the gas turbine is referred to as a front side (left side in Fig. 1) and the expansion device side is referred to as a rear side (right side in Fig. 1).
  • the rotor tail end 10 includes an end disk 12 in the form of a substantially circular disk having a disk center hole 13 and a substantially cylindrical hollow shaft portion 14.
  • a steam passage member 20 for supplying cooling steam is welded to the disk center hole 13.
  • the end disk 12 is provided with a plurality of through holes 12b (not shown) which are spaced at an equal distance in the circumferential direction about the center axis O in the longitudinal direction of the rotor assembly.
  • Turbine spindle bolts (not shown) are inserted in the through holes 12b while the end disk 12 is in contact at its front end surface 12a with another disk (not shown) and the turbine spindle bolts are fastened by nuts (not shown), so that a rotor assembly which rotates as a unit, while supporting turbine rotor blades (not shown) is formed.
  • the rotor assembly constructed as above is rotatably supported at the rotor tail end 10 by a bearing 24.
  • the bearing 24 is comprised of a bearing pad 24a, and seal portions 26 provided on opposite sides of the bearing pad 24a.
  • the bearing 24 forms a journal bearing.
  • the seal portions 26 include brackets 26a which are adapted to mount seal members 26c to the bearing pad 24a.
  • the rotor tail end 10 is provided with a rotor tail end center hole 15 which is coaxial with the disk center hole 13 and whose diameter is greater than the diameter of the disk center hole 13.
  • a cylindrical thermal sleeve 16 is inserted in the rotor tail end center hole 15.
  • the front end of the thermal sleeve 16 (left end in Fig. 1) is welded to the rotor tail end center hole 15 and the rear end (right end in Fig. 1) is welded to the rear end of the shaft portion 14.
  • the outer diameter of the thermal sleeve 16 is smaller than the inner diameter of the rotor tail end center hole 15 and a thermal insulation gas layer 18 is formed therebetween.
  • the thermal insulation gas layer 18 is filled with dry gas or inert gas such as air or argon.
  • the thermal sleeve 16 is provided on its rear end with a bent portion 16a which is adapted to absorb the thermal stress and in particular the compression stress when a temperature difference is caused between the shaft portion 14 and the thermal sleeve 16 whose temperature is increased in accordance with the operation of the gas turbine. More preferably, the thermal sleeve 16 is welded to the shaft portion 14 while the thermal sleeve is tensed in the axial direction so that a pre-tension is applied thereto. Consequently, when a temperature difference is caused between the thermal sleeve 16 and the shaft portion 14, in accordance with operation of the gas turbine, the compression stress can be reduced.
  • the thermal sleeve 16 is inserted between the steam passage member 20 and the shaft portion 14 so that the thermal insulation gas layer 18 is formed between the thermal sleeve 16 and the inner surface of the rotor tail end center hole 15 of the shaft portion 14. Consequently, when the gas turbine operates and the cooling steam for cooling the turbine rotor blades flows, the heat transfer to the shaft portion 14 is restricted, thus resulting in no or little thermal deformation of the shaft portion 14.
  • the thermal sleeve 16 is welded to the shaft portion 14 with a pre-tension, the thermal stress caused in the thermal sleeve 16 is reduced and thus the deformation thereof can be prevented.
  • the thermal sleeve 16 is provided with the bent portion 16a at the rear end thereof, the thermal stress which cannot be absorbed by the application of the pre-tension can be absorbed by the deformation of the bent portion 16a. Thus, deformation of the cylindrical portion of the thermal sleeve 16 can be avoided.
  • the thermal insulation gas layer 18 is isolated gas-tightly and liquid-tightly from the outside, so that no steam can enter from the outside. Moreover, since the thermal insulation gas layer 18 is filled with a dry gas, no drain due to the condensation of the steam occurs even if the temperature drops during the stoppage of the gas turbine.
  • Figs. 2 and 3 shows a second embodiment not falling under the scope of the claims.
  • the rotor tail end 10 is comprised of a substantially circular disk portion 12 which forms an end disk and a substantially cylindrical hollow shaft portion 14.
  • a disk center hole 13 of a rotor and a rotor tail end center hole 15 are also formed in the rotor tail end along the longitudinal center axis O.
  • the rotor tail end center hole 15 is coaxial to the disk center hole 13 and has a diameter greater than the diameter of the disk center hole 13.
  • the disk portion 12 is provided with a plurality of through holes (not shown) which are spaced at an equal distance in the circumferential direction about the center axis O.
  • Turbine spindle bolts (not shown) are inserted in the through holes while the disk portion 12 is in contact at its front end surface 12a with another disk (not shown) and the turbine spindle bolts are fastened by nuts (not shown), so that a rotor assembly which supports the turbine rotor blades (not shown) and rotates together therewith is formed.
  • a steam passage member 20 is provided in the rotor disk center hole 13 to form a passage for the steam for cooling the turbine rotor blades.
  • the inner surface of the rotor tail end center hole 15 of the shaft portion 14 of the rotor and the steam passage member 20 define therebetween a passage for recovering the steam for cooling the turbine rotor blades.
  • the rotor assembly constructed as above is rotatably supported at the tail end 10 by the bearing 24 as in the first embodiment.
  • the shaft portion 14 is provided with a plurality of shaft portion cooling air passages comprised of radially extending cooling air inlet passages 31a, axially extending main air passages 31b, and radially extending cooling air outlet passages 31c.
  • the shaft portion cooling air passages are spaced at an equal distance in the circumferential direction about the center axis O.
  • the main air passages 31b can be formed, for example, by drilling the rotor at the end thereof to form axially extending blind holes and thereafter closing the open ends of the blind holes by welds 31d.
  • a cooling air introduction device 32 is provided to face the cooling air inlet passages 31a.
  • the cooling air introduction device 32 is comprised of an air introduction passage 32a provided on a stationary part of the gas turbine, such as a casing (not shown), and a seal portion 32b provided on the inner circumferential surface of the air introduction portion 32a.
  • the air introduction portion 32a and the seal portion 32b are respectively provided with air passages 32c and 32d which are connected to the cooling air inlet passages 31a and which are spaced at an equal distance in the circumferential direction, so that the cooling air supplied from the cooling air supply source (not shown) can be introduced into the cooling air inlet passages 31a.
  • a cooling air discharge device 33 is provided to face the cooling air outlet passages 31c.
  • the cooling air discharge device 33 is comprised of an air discharge portions 33a provided on the stationary part of the gas turbine, such as the casing (not shown), and a seal portion 33b provided on the inner circumferential surface of the air discharge portion 33a.
  • the air discharge portion 33a and the seal portion 33b are respectively provided with a plurality of air passages 33c and 33d which are connected to the cooling air discharge passages 31c and which are spaced at an equal distance in the circumferential direction.
  • the air from the cooling air introduction device 32 is fed to a plurality of shaft portion cooling air passages 31a, 31b and 31c to cool the rotor tail end 10 and is discharged to the outside of the gas turbine.
  • the shaft portion 14 is provided with a plurality of shaft portion cooling air passages 31a, 31b and 31c in which the cooling air passes, when the turbine rotor blade cooling steam flows in the steam passage member 20 in accordance with the operation of the gas turbine, the shaft portion 14 is cooled at the portion thereof in the vicinity of the surface by the cooling air which passes in the shaft portion cooling air passages 31a, 31b and 31c and, thus, a thermal deformation of the shaft portion 14 can be minimized or restricted.
  • a plurality of shaft portion cooling air passages 31a, 31b and 31c are formed by directly drilling the shaft portion 14.
  • the shaft portion cooling air passages are formed between the outer peripheral surface of the shaft body portion and the sleeve by fitting a sleeve on an outer surface of the shaft body portion of the rotor tail end.
  • the rotor tail end 10 of the third embodiment is comprised of a substantially circular disk portion 12 which defines an end disk, a substantially cylindrical hollow shaft body portion 14, and a sleeve 17 which is fitted on the shaft body portion 14.
  • the tail end center hole 15 of the rotor is formed to extend along the longitudinal center axis O.
  • a rotor assembly is formed and is rotatably supported by a bearing 24 similar to that in the previous embodiments at the rotor tail end 10. Namely, the shaft body portion 14 and the sleeve 17 fitted thereon define the shaft portion in the previous embodiments.
  • the sleeve 17 is comprised of a substantially cylindrical member having an inner peripheral surface 17a having an inner diameter equal to the diameter of the shaft portion 14, and an outer peripheral surface 17b having an outer diameter equal to shaft portion of the rotor assembly which is rotatably supported by the bearing 24.
  • the inner peripheral surface 17a is provided with a plurality of axially extending semi-circular grooves 17c.
  • the sleeve 17 is fitted on the outer peripheral surface of the shaft body portion 14 and, thereafter, the annular end plate 17d is secured to the end of the shaft body portion 14 by means of bolts 17e.
  • the end plate 17d is provided with a plurality of cooling air outlet passages 31c which can be connected to main air passages 17f formed between the outer peripheral surface of the shaft body portion 14 and the grooves 17c of the sleeve 17, when assembled as shown in Fig. 4.
  • the shaft portion 14 is provided with a plurality of cooling air inlet passages 31a in the vicinity of the proximal end thereof, which can be connected to the main air passages 17f.
  • the cooling air inlet passages 31a, the main air passages 17f and the cooling air outlet passages 31c form a plurality of shaft portion cooling air passages.
  • the shaft portion cooling air passages 31a, 17f, and 31c are spaced at an equal distance in the circumferential direction with respect to the center axis O.
  • a cooling air introduction device 32 is provided to face the cooling air inlet passages 31a and a cooling air discharge device 33 is provided to face the cooling air outlet passages 31c.
  • the air from the cooling air introduction device 32 is fed to the shaft portion cooling air passages 31a, 17f and 31c to cool the rotor tail end 10 and is discharged to the outside of the gas turbine.
  • the shaft portion cooling air passages 31a, 17f and 31c in which the cooling air can be passed are formed between the shaft body portion 14 and the sleeve 17, the sleeve 17 which forms a part of the shaft portion of the rotor tail end is cooled when the rotor blade cooling steam is fed in the steam passage member 20 in accordance with the operation of the gas turbine. Consequently, the thermal deformation of the shaft portion is minimized or restricted.
  • Figs. 6 through 8 describe the embodiment of the present invention.
  • the rotor tail end 10 of the embodiment of the invention is comprised of a substantially circular disk portion 12 which defines an end disk, and a substantially cylindrical hollow shaft portion 14.
  • the disk center hole 13 of the rotor and the rotor tail end center hole 15 are formed to extend along the longitudinal center axis O.
  • the rotor tail end center hole 15 is coaxial to the disk center hole 13 and has a diameter greater than the diameter of the disk center hole 13.
  • the disk portion 12 is provided with a plurality of through holes (not shown) which are spaced at an equal distance in the circumferential direction about the center axis O.
  • Turbine spindle bolts (not shown) are inserted in the through holes while the disk portion 12 is in contact at its front end surface 12a with another disk (not shown), the turbine spindle bolts are fastened by nuts (not shown), so that a rotor assembly which supports the turbine rotor blades (not shown) and rotates together therewith is formed.
  • a steam passage member 20 is provided in the rotor disk center hole 13 to form a passage for the steam for cooling the turbine rotor blades.
  • the inner surface of the rotor tail end center hole 15 of the shaft portion 14 of the rotor and the steam passage member define therebetween a passage for recovering the steam for cooling the turbine rotor blades.
  • the rotor assembly constructed as above is rotatably supported at the tail end 10 by the bearing 24.
  • the bearing 24 in this embodiment according to the invention is comprised of a bearing pad 24a and seal portions 26 provided on opposite sides of the bearing pad 24a.
  • the seal portions 26 include seal members 26c and brackets to mount the seal members 26c to the bearing pad 24a.
  • the brackets include radial securing portions 26a mounted to the bearing pad 24a and ledges 26b connected to the radial securing portions 26a, so that the brackets are L-shaped in a cross section.
  • the seal members 26c are greater in the width, i.e. in the size in the axial direction, than those of the embodiments illustrated in Figs. 1 through 5. Accordingly, the brackets of the bearing 24 are provided with the ledges 26b which extend in the axial direction, unlike the previous embodiments shown in Figs. 1 through 5.
  • the bearing pad is provided with an oil passage (not shown) extending therethrough in the radial direction, so that a lubricant is supplied through the oil passage to lubricate the gap between the shaft portion of the rotor assembly and the bearing and to cool the gap between the shaft portion and the bearing pad.
  • the seal member reduces the leakage of lubricant from the gap between the shaft portion and the bearing pad, so that the lubrication between the shaft portion and the bearing pad can be promoted.
  • the seal members 26c which are greater in width in the axial direction than the seal members of the prior art is used to resolve the problems of the prior art mentioned above. Namely, the seal members 26c must be long enough to maintain the surface temperature of the shaft portion 14 at the constant low temperature TL, in the area of the axial length L0 of the bearing pad 24a, i.e., in the surface area of the shaft portion 14 opposed to the bearing pad.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sliding-Contact Bearings (AREA)
  • Sealing Devices (AREA)

Claims (1)

  1. Rotorhinterende (10) einer Gasturbine mit
    - einer Lagerstruktur zum Lagern eines Wellenteils (14) des Rotorhinterendes,
    - einer Rotoranordnung der Gasturbine mit einer Mittelachse (O);
    - Rotorschaufeln der Gasturbine;
    - einem Dampfdurchgang (20), der sich entlang der Mittelachse (O) erstreckt, zum Zuführen und Rückgewinnen von Dampf zum Kühlen der Rotorschaufeln;
    - einem Lagerklotz (24a), der ein Zapfenlager (24) bildet;
    - und Abdichtungsteilen (26), die auf entgegengesetzten Seiten des Lagerklotzes (24a) in der axialen Richtung vorgesehen sind, um den Austritt eines Schmiermittels zum Schmieren eines Raums zwischen dem Lagerklotz und dem Wellenteil zu verhindern, wobei die Abdichtungsteile (26) Dichtungselemente (26c) und Stützen, um die Dichtungselemente (26c) an dem Lagerklotz (24a) anzubringen, umfassen
    - dadurch gekennzeichnet, dass
    - die Stützen radiale Befestigungsteile (26a), die am Lagerklotz (24a) angebracht sind, und Leisten (26b), die mit den radialen Befestigungsteilen (26a) verbunden sind, umfassen und die Stützen in einem Querschnitt L-förmig sind,
    - die Breite des Abdichtungsteils (26) in der axialen Richtung derart ist, dass die Oberflächentemperatur des Wellenteils (14) des Rotorhinterendes durch das Schmiermittel innerhalb der Breite (L0) des Lagerklotzes (24a) in der axialen Richtung unter einer vorbestimmten Temperatur gehalten wird.
EP04023742A 2000-09-26 2001-08-25 Wellen- und Lageranordnung für eine dampfgekühlte Gasturbine Expired - Lifetime EP1496198B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP2000292763 2000-09-26
JP2000292763A JP4690531B2 (ja) 1999-09-27 2000-09-26 ガスタービンのロータ尾端部の軸構造
EP01120371A EP1191188B1 (de) 2000-09-26 2001-08-25 Wellenanordnung für eine dampfgekühlte Gasturbine

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
EP01120371A Division EP1191188B1 (de) 2000-09-26 2001-08-25 Wellenanordnung für eine dampfgekühlte Gasturbine

Publications (3)

Publication Number Publication Date
EP1496198A2 EP1496198A2 (de) 2005-01-12
EP1496198A3 EP1496198A3 (de) 2005-01-19
EP1496198B1 true EP1496198B1 (de) 2008-01-23

Family

ID=18775653

Family Applications (3)

Application Number Title Priority Date Filing Date
EP01120371A Expired - Lifetime EP1191188B1 (de) 2000-09-26 2001-08-25 Wellenanordnung für eine dampfgekühlte Gasturbine
EP04023741A Expired - Lifetime EP1496197B1 (de) 2000-09-26 2001-08-25 Wellenanordnung für eine dampfgekühlte Gasturbine
EP04023742A Expired - Lifetime EP1496198B1 (de) 2000-09-26 2001-08-25 Wellen- und Lageranordnung für eine dampfgekühlte Gasturbine

Family Applications Before (2)

Application Number Title Priority Date Filing Date
EP01120371A Expired - Lifetime EP1191188B1 (de) 2000-09-26 2001-08-25 Wellenanordnung für eine dampfgekühlte Gasturbine
EP04023741A Expired - Lifetime EP1496197B1 (de) 2000-09-26 2001-08-25 Wellenanordnung für eine dampfgekühlte Gasturbine

Country Status (4)

Country Link
US (1) US6688847B2 (de)
EP (3) EP1191188B1 (de)
CA (1) CA2356479C (de)
DE (3) DE60117077T2 (de)

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US7090393B2 (en) * 2002-12-13 2006-08-15 General Electric Company Using thermal imaging to prevent loss of steam turbine efficiency by detecting and correcting inadequate insulation at turbine startup
FR2892148B1 (fr) * 2005-10-19 2011-07-22 Snecma Fourreau d'arbre de turboreacteur et turboreacteur comportant ce fourreau
JP5129633B2 (ja) * 2008-03-28 2013-01-30 三菱重工業株式会社 冷却通路用カバーおよび該カバーの製造方法ならびにガスタービン
US10495353B2 (en) * 2012-05-28 2019-12-03 The University Of Western Ontario Mechanism for enhanced energy extraction and cooling of pressurized gas at low flow rates
US20140010648A1 (en) * 2012-06-29 2014-01-09 United Technologies Corporation Sleeve for turbine bearing stack
US20140119887A1 (en) * 2012-11-01 2014-05-01 United Technologies Corporation Fluid-cooled seal arrangement for a gas turbine engine
EP2971663B1 (de) 2013-03-13 2019-05-01 United Technologies Corporation Öltransferdurchgangsanordnung für eine welle eines gasturbinenmotors
CN109113809B (zh) * 2018-09-17 2023-09-19 苏州制氧机股份有限公司 气体轴承透平膨胀机
US11193389B2 (en) 2019-10-18 2021-12-07 Raytheon Technologies Corporation Fluid cooled seal land for rotational equipment seal assembly
KR20200081345A (ko) 2020-06-08 2020-07-07 (주)퍼니랜드 무인 자판기
CN114013818B (zh) * 2021-11-17 2023-07-04 嘉利特荏原泵业有限公司 一种汽轮机转子用运输和储存容器

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2768789B2 (ja) * 1990-03-05 1998-06-25 株式会社東芝 ガスタービンロータ
JPH07139635A (ja) * 1993-11-18 1995-05-30 Fuji Electric Co Ltd 回転機械軸受台のシールリング
JP3567065B2 (ja) * 1997-07-31 2004-09-15 株式会社東芝 ガスタービン
US6224327B1 (en) * 1998-02-17 2001-05-01 Mitsubishi Heavy Idustries, Ltd. Steam-cooling type gas turbine
JP4308388B2 (ja) * 1998-12-18 2009-08-05 ゼネラル・エレクトリック・カンパニイ タービンロータを蒸気冷却するためのボアチューブアセンブリ
JP4527824B2 (ja) 1998-12-22 2010-08-18 ゼネラル・エレクトリック・カンパニイ タービンロータの軸受用冷却系

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EP1496197B1 (de) 2008-11-26
US20020037216A1 (en) 2002-03-28
US6688847B2 (en) 2004-02-10
DE60136753D1 (de) 2009-01-08
DE60132642D1 (de) 2008-03-13
CA2356479C (en) 2005-07-19
EP1191188A2 (de) 2002-03-27
EP1496198A2 (de) 2005-01-12
CA2356479A1 (en) 2002-03-26
EP1496198A3 (de) 2005-01-19
EP1191188A3 (de) 2003-11-19
DE60117077T2 (de) 2006-07-13
EP1496197A1 (de) 2005-01-12
DE60117077D1 (de) 2006-04-20
EP1191188B1 (de) 2006-02-08

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